Mtu Aero Engines Ag

Marcin Rozak

Markus Schlemmer

Alexander Buck

The present invention relates to a blade rim segment for a turbomachine with at least one shroud band which extends along a segment of a circle and is connected in single-piece fashion with at least three blades, which extend radially from the shroud band and are configured to be hollow with at least one channel, wherein the blade rim segment is manufactured in a single piece by casting and directional solidification, and wherein at the outlet openings of the channels of the blades, the shroud band exhibits first reinforcement ribs that surround the opening and run axially, as well as at least one second reinforcement rib between at least the first reinforcement ribs, as well as a corresponding method for manufacturing a blade rim segment.

Blade rim segment for a turbomachine and method for manufacture

A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade () is situated, the guide blade () including at least one shroud configuration () having a radially outer shroud () and having a shroud holding device () with the aid of which the shroud () is secured on the housing, as well as including a turbine blade () extending radially inward from the shroud configuration (). The shroud holding device () or parts thereof include(s) at least one air passage channel (), which permits a flow passage through the shroud holding device (). The invention also relates to a guide blade () for placement on a housing of a gas turbine as well as a method for manufacturing such a guide blade ().

Growing community of inventors

Jaroslaw, Poland

Marcin Rozak